WO2018019074A1 - 空难逃生飞机 - Google Patents

空难逃生飞机 Download PDF

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Publication number
WO2018019074A1
WO2018019074A1 PCT/CN2017/090452 CN2017090452W WO2018019074A1 WO 2018019074 A1 WO2018019074 A1 WO 2018019074A1 CN 2017090452 W CN2017090452 W CN 2017090452W WO 2018019074 A1 WO2018019074 A1 WO 2018019074A1
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Prior art keywords
aircraft
fuselage
engine
jet engine
air crash
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PCT/CN2017/090452
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English (en)
French (fr)
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冯政尧
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冯政尧
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Publication of WO2018019074A1 publication Critical patent/WO2018019074A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages

Definitions

  • the present invention relates to an aircraft and, more particularly, to an airborne escape aircraft.
  • Aircraft is the most important and fastest type of modern transportation. From the structural analysis, the aircraft itself should also be the vehicle with the highest safety factor. However, since the operating area of the aircraft is high, there are many unpredictable factors. Even if the aircraft is thoroughly and thoroughly tested before each flight, it is still impossible to avoid the air disaster caused by many factors. Because the aircraft is running at high altitude, once the air crash occurs, the personnel inside the aircraft, especially the ordinary passengers in the passenger aircraft, rely on the guidance, comfort and guidance of the flight attendants, and still cannot make the passengers self-rescue. Therefore, once the plane crashes, almost It means the demise of hundreds of lives.
  • the core idea is similar to the scheme in the video mentioned above, that is, the aircraft body is made into a separable form, and the split solution is
  • the main body is made into a separate outer casing and a plurality of cabin units.
  • the head of the aircraft and the fuselage are blasted to form an exit of the cabin unit on the main body, and the cabin unit is controlled by the brake device. Slide the body out at a controlled sliding speed and open the parachute, cushioning airbag, etc. in a manner similar to that demonstrated in the video to allow the cabin unit to land safely.
  • the object of the present invention is to provide an air crash escape aircraft, which can provide additional flight power for the aircraft after the engine is turned off, stabilize the flight attitude of the aircraft, thereby causing the aircraft to land, so that passengers and crew members Rescued.
  • an air crash escape aircraft including an organic body and wings disposed on the left and right sides of the fuselage, the main engine is symmetrically disposed on the wing, and the special feature is:
  • the rear end of the fuselage is provided with a jet engine that is opened after the main engine is turned off, and the jet engine provides thrust to the aircraft.
  • the accident of the air crash is generally caused by the single engine and the double-fire stall of the main engine on the wing, so that the aircraft suddenly loses all or part of the power, and the flight of the aircraft becomes lost due to the loss of flight power.
  • an emergency jet engine is installed at the rear of the aircraft.
  • the jet engine can provide the aircraft with forward flight power.
  • the learning function can provide a certain lift for the aircraft. Under the action of lift, it can guarantee a slow decline.
  • the aircraft can perform emergency operation of the aircraft like normal flight conditions.
  • the pilot can control the aircraft's flight attitude and the flight power of the jet engine to achieve the purpose of landing the aircraft, thus protecting the valuable lives of passengers and crew.
  • the present invention is further configured such that the jet engine is located inside the rear end of the fuselage, and an air intake chamber communicating with the jet engine is disposed in the airframe, and the air intake chamber is uniformly disposed on the jet engine
  • An end cover opened before starting the end cover being rotatably connected to the fuselage near an end of the rear end of the fuselage, the end cover being connected with a control mechanism opened and closed by the end cover, the end cover being opened It is then opposite to the flight direction of the aircraft and is set at an acute angle.
  • the jet engine is disposed inside the tail end of the aircraft fuselage, and in order to provide good air supply to the jet engine at the time of starting, an air inlet chamber is arranged on the jet body, and a rotary connection is arranged on the air inlet chamber. End caps.
  • the end cover is opened by the control mechanism, and the end cover is opened and fixed at an acute angle to the direction of the fuselage. At this time, the end cover can guide the airflow, thereby guiding the airflow into the air intake chamber. Enter the engine to ensure the normal operation of the aircraft engine.
  • control mechanism comprises a connecting rod rotatably connected to an inner surface of the end cover, the connecting rod is rotatably connected with a slider, and the sliding rod is arranged in the middle of the inlet chamber The connection is connected, and the slider is connected with a hydraulic mechanism for controlling the movement of the slider.
  • the hydraulic mechanism provides power for the movement of the slider, thereby moving the slider, and the slider moves to drive the link at the same time, thereby driving the end cover to move, and the movement of the link is caused by the end cover being rotatably connected with the body. It can drive the rotation of the end cover to achieve the purpose of controlling the opening and closing of the end cover.
  • the invention is further provided that the inlet chamber is contracted in a direction from the head to the end of the fuselage.
  • the air inlet chamber is arranged in a contracted shape from the head to the tail end of the aircraft fuselage, and the contracted shape of the air inlet chamber can guide the air, so that the air entering the air inlet chamber enters the air jet.
  • the engine it is conducive to the normal operation of the aircraft.
  • the invention is further configured such that the engine is located below the fuselage, the jet engine is coupled to a mounting bracket, and the mounting bracket is coupled below the rear end of the fuselage.
  • the jet engine is disposed under the rear end of the fuselage, and the jet engine is connected to the fuselage through the bracket, and the jet engine can not only provide forward power to the fuselage, but also generate a certain torque.
  • the aircraft's nose is facing up, the nose is up to avoid the rapid decline of the aircraft, and the adjustment of the wing can increase the lift and further slow down the aircraft's falling speed.
  • the invention is further provided that the jet engine can be replaced with a rocket engine.
  • the jet engine is replaced with a rocket engine, and the rocket launch can provide a large power in a short period of time, thereby providing a large thrust while the main engine of the aircraft is turned off, thereby ensuring the stability of the flight state of the aircraft.
  • the pilot can further adjust the flight attitude of the aircraft, so that the aircraft can slide and make a forced landing.
  • the invention is further provided that the rocket engine is coupled to the end of the fuselage end.
  • the rocket launcher can be installed at The inside of the end of the fuselage end not only saves space, but also provides more concentrated thrust for the fuselage.
  • the invention is further provided that the front end of the jet engine is connected to a shroud arranged in a streamlined manner for reducing normal flight resistance, the shroud being opened before the jet engine needs to be opened.
  • the jet engine since the jet engine is used as an emergency engine, it does not need to be opened or operated during the normal flight of the aircraft, so a streamlined flow guide is arranged at the front end of the jet engine to prevent air from entering the jet.
  • the jet engine not only can the jet engine be placed in a changing environment, but the streamlined shroud can further reduce the resistance loss caused by the jet engine, thereby saving aircraft fuel.
  • the invention is further provided that the bottom of the fuselage is further provided with at least one inflatable unit for buffering the impact force of the fuselage when the aircraft is forced to land.
  • the air unit is arranged to buffer when the aircraft contacts the ground, thereby avoiding a hard collision between the aircraft and the ground, thereby ensuring passengers to a greater extent. And the safety of the crew.
  • the invention is further provided that the fuselage and or the wing are evenly provided with a plurality of parachutes hidden in the arrangement.
  • the jet engine is turned off, and the parachute on the fuselage and the wing is opened, so that the airframe enters the free fall state, and the parachute can be improved.
  • the relative resistance of the aircraft to the air which further reduces the descending speed of the aircraft fuselage, thereby ensuring that the fuselage falls to the landing point at a lower speed and improves the success rate of the landing.
  • the present invention has the following beneficial effects: the present invention can provide power for the flight of the aircraft by starting the jet engine or the rocket engine when the aircraft engine is single-fired or completely extinguished, thereby providing conditions for the forced landing of the aircraft, To the extent of ensuring the safety of passengers and crew members, to avoid the occurrence of air crashes.
  • Embodiment 1 is a schematic structural view of Embodiment 1;
  • FIG. 2 is a schematic structural view of the first embodiment after opening the end cover
  • FIG. 3 is a schematic structural view of a control mechanism of Embodiment 1;
  • Embodiment 4 is a schematic structural view of Embodiment 2;
  • Figure 5 is a schematic structural view showing the opening of the parachute of the second embodiment
  • Fig. 6 is a schematic structural view of the third embodiment.
  • Embodiment 1 An air crash escape aircraft, as shown in FIG. 1 , FIG. 2 and FIG. 3 , includes a fuselage 1 , and the organic wing 2 is symmetrically mounted on both sides of the fuselage 1 , and the wing 2 is symmetrically mounted for the aircraft.
  • Powered main engine 3 At the same time, the tail of the aircraft is also provided with a horizontal tail 6 and a vertical tail 7, and the horizontal tail 6 and the vertical tail 7 are respectively provided with an elevator 12 and a rudder 13.
  • the elevator 12 is used to adjust the pitch state of the aircraft, and the rudder 13 is used to adjust the flight direction of the aircraft.
  • the tail end of the aircraft fuselage 1 is provided with a jet engine 4, and the jet direction of the jet engine 4, that is, the thrust direction provided by the jet engine 4, is parallel to the direction of the fuselage 1.
  • the jet engine 4 is disposed inside the rear end of the fuselage 1.
  • an air intake chamber communicating with the jet engine 4 is disposed at the front end of the jet engine 4 in the fuselage 1 of the aircraft, at the intake air.
  • An end cover 14 is evenly disposed on the outer wall of the chamber. One end of the end cover 14 near the rear end of the body 1 is rotatably connected to the body 1.
  • the end cover 14 is opened and closed by the pilot by the control mechanism 15, and the control mechanism 15 includes the end.
  • the inner surface of the cover is rotatably connected to the connecting rod 151, the connecting rod 151 is rotatably connected with the slider 152, and the slider 152 and the sliding rod 153 disposed in the middle of the air inlet chamber
  • a slip connection is connected to the slider with a hydraulic mechanism 154 for controlling the movement of the slider.
  • the end cover 14 is opened by the hydraulic mechanism and disposed at an acute angle to the flight direction of the aircraft, while the inner surface of the end cover 14 can guide the air flow so that the airflow enters the intake chamber.
  • the intake chamber is set to be contracted in the direction of the airflow entering, thereby providing a guiding effect for the normal operation of the jet engine 4.
  • the pilot manually controls the aircraft and adjusts the flight attitude of the aircraft, while at the same time opening the aircraft's jet engine 4, at which time the aircraft engine can provide flight power to the aircraft, at which time the pilot controls the wing 2 allows the wing 2 to provide as much lift as possible for the aircraft, thereby slowing down the speed of the aircraft.
  • the aircraft is powered by the power of the jet engine 44.
  • the pilot can adjust the pitch state and flight direction of the aircraft by controlling the elevator 12 or the rudder 13 of the aircraft.
  • the pilot can choose the landing site. When the aircraft flies to the landing site, the aircraft can make a forced landing. When the aircraft is about to come into contact with the ground during the landing, the inflatable unit 10 is opened, thereby reducing the impact force on the ground when the aircraft is forced to land, and further ensuring the safety of the passengers. To avoid the occurrence of air crashes.
  • Embodiment 2 An air crash escape aircraft, as shown in FIG. 4 and FIG. 5, includes a fuselage 1, and the organic wing 2 is symmetrically mounted on both sides of the fuselage 1, and the wing 2 is symmetrically mounted to power the aircraft.
  • Main engine 3. A plurality of parachutes 11 hidden in a setting are also uniformly disposed on the body 1 and the wing 2.
  • the tail of the aircraft is also provided with a horizontal tail 6 and a vertical tail 7, and the horizontal tail 6 and the vertical tail 7 are respectively provided with an elevator 12 and a rudder 13.
  • the elevator 12 is used to adjust the pitch state of the aircraft, and the rudder 13 is used to adjust the flight direction of the aircraft.
  • a mounting bracket 8 is mounted below the rear end of the aircraft fuselage 1.
  • the jet engine 4 is mounted on the mounting bracket 8, and the jet direction of the jet engine 4, that is, the thrust direction provided by the jet engine 4, is parallel to the direction of the fuselage 1.
  • the jet engine 4 is placed below the rear end of the fuselage 1, and the jet engine 4 is connected through the bracket Connected to the fuselage 1, at this time, the jet engine 4 can not only provide forward power to the fuselage 1, but also generate a certain torque, so that the nose of the aircraft is upward, and the head is upwards to avoid rapid descending of the aircraft.
  • the adjustment of the wing 2 can increase the lift and further slow down the falling speed of the aircraft.
  • a flow guide 9 is provided at the front end of the jet engine 4, and the shroud 9 is arranged in a streamlined manner, thereby reducing the resistance of the flight and thereby saving the aircraft.
  • the fuel can be opened by the pilot's manual control before the jet engine 4 is opened.
  • the bottom of the aircraft fuselage 1 can also be provided with an inflator unit 10 for buffering the impact force when the aircraft is forced to land.
  • the pilot manually controls the aircraft and adjusts the flight attitude of the aircraft, opening the shroud 9 and simultaneously opening the jet engine 4 of the aircraft, at which time the aircraft engine can provide flight power to the aircraft.
  • the pilot controls the wing 2 so that the wing 2 can provide as much lift as possible for the aircraft, thereby slowing down the speed of the aircraft.
  • the aircraft is powered by the power of the jet engine 4.
  • the pilot can adjust the pitch state and flight direction of the aircraft by controlling the elevator 12 or the rudder 13 of the aircraft.
  • the pilot can choose the landing site. When the aircraft flies to the landing site, the aircraft can make a forced landing.
  • Embodiment 3 An air crash escape aircraft, as shown in FIG. 6, is different from the second embodiment in that the jet engine 4 is replaced with a rocket engine 5, and the rocket engine 5 is connected at an end position of the tail end of the aircraft.
  • the rocket launch can provide greater power in a shorter period of time, providing a large thrust while the main engine 3 is turned off, ensuring that the aircraft is instantaneous. The thrust will not suddenly decrease, thus ensuring the stability of the flight state of the aircraft. Due to the short working time of the rocket engine 5, its main function is to avoid the influence of the flameout of the main engine 3 on the flight attitude of the aircraft. The pilot can complete the forced landing process by controlling the aircraft to taxi, thus avoiding air crashes.

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

一种空难逃生飞机，其技术方案要点是包括有机身（1）以及设置于机身左右两侧的机翼（2），所述机翼上对称设置有主发动机（3），所述机身的尾端设置有在所述主发动机熄火后打开的喷气发动机（4），所述喷气发动机为飞机提供推力

Description

空难逃生飞机 技术领域
本发明涉及一种飞机，更具体的说，它涉及一种空难逃生飞机。
背景技术
飞机，是现代交通工具中最为重要、最为快捷的一种，从构造上分析，飞机本身也应当是安全系数最高的一种交通工具。然而，由于飞机的运行区域为高空，不可预测的因素很多，即使每次飞行前都对飞机进行全面细致的检测，依然无法避免由于多方面因素导致的空难。而由于飞机运行于高空，一旦发生空难，飞机内的人员，尤其是客机内的普通乘客，依赖空乘人员的疏导、安抚与指导，依然无法使乘客具有自救能力，因此，一旦飞机失事，几乎就意味着成百上千条生命的消逝。
从飞机被发明以来，除去对飞机制造、控制以及驾飞行模拟器的研究外，对于飞机如何应对空难的研究也层出不穷，其中较为主流的是如http://www.le.com/ptv/vplay/24777237.html？ch＝360kandsp网站视频中所公开的方式，即：以飞机分体的方式将客舱与飞机的其他位置分离，并给客舱顶部配备降落伞、喷气减速装置，给客舱底部设置缓冲气囊，以使客舱可以在路面或者海面安全降落，挽救客舱的乘客的生命。又如授权公告号为CN1148306C的发明专利授权文本中所公开的技术方案，其核心思想与上述提到的视频中的方案近似，即将飞机主体做成可分体的形式，其分体的方案是将主体做成相互独立的外壳和若干客舱单元，发生危险时，飞机的头部与机身之际炸开，以在主体上形成一个客舱单元滑出的出口，客舱单元在制动装置的控制下以可控的滑动速度滑出主体，并按照类似于视频中演示的方式打开降落伞、缓冲气囊等，以使客舱单元安全着陆。
上述技术方案虽然能够在将客舱分离，并逐渐下降，但是若机身飞行的速度较大，使用降落伞会改变机身的位置状态从而使得机身不平稳，会危及到乘客和乘务人员的生命安全。
飞机空难的产生多数是由于发动机熄火，在飞机发动机单发熄火或是双发熄火，发动机失去部分动力或是全部动力而造成飞机飞行姿态紊乱，难以控制，导致飞机掉落造成。因此，若能够在飞机发动机熄火后，为飞机提供滑行的动力，使飞机能够通过滑行进行迫降，因而能够为飞机乘客及乘务人员提供生存的可能性。
发明内容
针对现有技术存在的不足，本发明的目的在于提供一种空难逃生飞机，其在发动机熄火后，能够为飞机提供额外的飞行动力，稳定飞机飞行姿态，从而使得飞机迫降，使得乘客和乘务人员获救。
为实现上述目的，本发明提供了如下技术方案：一种空难逃生飞机，包括有机身以及设置于机身左右两侧的机翼，所述机翼上对称设置有主发动机，其特在于：所述机身的尾端设置有在所述主发动机熄火后打开的喷气发动机，所述喷气发动机为飞机提供推力。
通过采用上述技术方案，空难事故的发生一般是由于机翼上的主发动机单发和双发熄火，而使得飞机突然失去全部动力或是部分动力，由于失去了飞行动力，因此飞机的飞行变得不可控，因此难以控制飞机进行迫降。因此在飞机的尾部设置应急的喷气发动机，当主发动机失去全部或是部分动力时，打开应急的喷气发动机，喷气发动机能够为飞机提供向前飞行的动力，当飞机向前飞行由于机翼的空气动力学作用，能够为飞机提供一定的升力，在升力的作用下，能够保障缓慢下降，此时飞机可以像正常飞行状态时进行飞机的应急操作， 飞行员能够通过控制飞机的飞行姿态和喷气发动机的飞行动力，达到使得飞机迫降的目的，从而保障乘客和乘务人员的宝贵生命。
本发明进一步设置为：所述喷气发动机位于所述机身尾端的内部，所述机身内设置有与所述喷气发动机连通的进气室，所述进气室上均匀设置有能够在喷气发动机启动前打开的的端盖，所述端盖靠近所述机身的尾端的一端转动连所述机身，所述端盖连接有由于所述端盖启闭的控制机构，所述端盖打开后与所述飞机飞行方向相对且呈锐角设置。
通过采用上述技术方案，将喷气发动机设置在飞机机身尾端的内部，为了对喷气发动机在启动时进行良好的供气，在喷气机身上设置进气室，同时在进气室上设置转动连接的端盖。当在主发动机熄火时，通过控制机构打开端盖，端盖打开后并将其固定与机身方向呈锐角设置，此时端盖能够对气流提供导向作用，进而将气流导向至进气室内，进入发动机，从而保障飞机发动机正常的运行。
本发明进一步设置为：所述控制机构包括所述端盖的内表面转动连接的连杆，所述连杆转动连接有滑块，所述滑块与所述进气室中部设置的滑杆滑移连接，所述滑块连接有用于控制所述滑块移动的液压机构。
通过采用上述技术方案，液压机构为滑块的移动提供动力，因而使得滑块移动，滑块移动同时带动连杆，进而带动端盖移动，由于端盖与机身转动连接，因此连杆的移动能够带动端盖的转动，从而达到控制端盖启闭的目的。
本发明进一步设置为：所述进气室在所述机身从头部到尾端方向上呈收缩设置。
通过采用上述技术方案，将进气室从飞机机身的头部到尾端设置成收缩形状，收缩形状的进气室能够对空气产生导向作用，从而使得进入进气室的空气都进入到喷气发动机中，有利于飞机的正常工作。
本发明进一步设置为：所述发动机位于所述机身下方，所述喷气发动机连接有安装支架，所述安装支架连接在所述机身尾端的下方。
通过采用上述技术方案，将喷气发动机设置在机身尾端的下方，并且通过支架将喷气发动机连接在机身上，此时喷气发动机不仅能够为机身提供向前的动力，同时能够产生一定的力矩，使得飞机的机头朝上，机头朝上能够避免飞机快速的下降，同时通过机翼的调节能够增大升力进一步减缓飞机的下落速度。
本发明进一步设置为：所述喷气发动机可更换为火箭发动机。
通过采用上述技术方案，将喷气发动机更换为火箭发动机，火箭发动能够在较短的时间内，提供较大的动力，因而能够在飞机主发动机熄火的同时提供大推力，从而保证飞机飞行状态的稳定，在失去火箭发动机的动力后，由于飞机飞行状态稳定，因而飞行员能够通过进一步调整飞机的飞行姿态，使得飞机能够滑行进行迫降。
本发明进一步设置为：所述火箭发动机连接在所述机身尾端的端部。
通过采用上述技术方案，由于火箭发动机在启动时不需要空气的参与，因而不需要为火箭发动机提供进气口的类似结构，因此火箭发动机的安装要求更小，因此，可以将火箭发动架安装在机身尾端的端部的内部，不仅节省空间，同时为机身提供的推力更加的集中。
本发明进一步设置为：所述喷气发动机的前端连接有呈流线型设置用于减小正常飞行时阻力的导流罩，所述导流罩在需要打开所述喷气发动机前打开。
通过采用上述技术方案，由于喷气发动机作为应急使用的发动机，其在正常飞机飞行的过程中是不需要进行打开或工作的，因此在喷气发动机的前端设置流线型设置的导流罩，避免空气进入喷气发动机中，不仅能够改变喷气发动机的放置环境，同时流线型设置的导流罩能够进一步减小喷气发动机带来的阻力损失，从而达到节省飞机燃油的目的。
本发明进一步设置为：所述机身的底部还设置有至少一个用于在飞机迫降时缓冲所述机身冲击力的充气单元。
通过采用上述技术方案，当飞机在进行迫降且没有良好的降落环境时，通过设置充气单元，在飞机与地面进行接触时进行缓冲，避免飞机和地面产生硬性的碰撞，从而更大程度上保障乘客和乘务人员的生命安全。
本发明进一步设置为：所述机身和或所述机翼上还均匀设置有隐藏设置的若干降落伞。
通过采用上述技术方案，当机身飞行到具有降落条件的场地时，控制飞机的高度后，关闭喷气发动机，同时打开机身和机翼上的降落伞，使得机身进入自由下落状态，降落伞能够提高飞机与空气的相对的阻力，从而进一度降低飞机机身的下降速度，从而保障机身以一个较低的速度降落到降落点，提高降落的成功率。
综上所述，本发明具有以下有益效果：本发明在飞机发动机单发熄火或是全部熄火时，能够通过启动喷气发动机或火箭发动机为飞机的飞行提供动力，从而为飞机的迫降提供条件，最大程度上保障乘客和乘务人员的生命安全，避免空难事故的发生。
附图说明
图1为实施例一的结构示意图；
图2为实施例一打开端盖后的结构示意图；
图3为实施例一的控制机构的结构示意图；
图4为实施例二的结构示意图；
图5为实施例二降落伞打开的结构示意图；
图6为实施例三的结构示意图。
图中：1、机身；2、机翼；3、主发动机；4、喷气发动机；5、火箭发动机；6、水平尾翼；7、垂直尾翼；8、安装支架；9、导流罩；10、充气单元；11、降落伞；12、升降舵；13、方向舵；14、端盖；15、控制机构；151、连杆；152、滑块；153、滑杆；154、液压机构。
具体实施方式
下面结合附图对本发明作进一步详细说明。
实施例一：一种空难逃生飞机，如图1、图2和图3所示，包括机身1，在机身1的两侧对称的安装有机翼2，机翼2上对称安装有为飞机提供动力的主发动机3。同时飞机的尾部还设置有水平尾翼6和垂直尾翼7，水平尾翼6和垂直尾翼7上分别设置有升降舵12和方向舵13。其中升降舵12用于调整飞机的俯仰状态，方向舵13用于调整飞机的飞行方向。
飞机机身1的尾端设置有喷气发动机4，喷气发动机4的喷气方向即喷气发动机4提供的推力方向与机身1的方向平行。喷气发动机4设置在机身1尾端的内部，为了使得发动机在工作时能够进行正常供气，在飞机的机身1内喷气发动机4的前端设置与喷气发动机4连通的进气室，在进气室上的外壁上均匀设置端盖14，端盖14靠近机身1的尾端的一端和机身1转动连接，端盖14通过控制机构15由飞行员操作能够完成开启和关闭，控制机构15包括端盖的内表面转动连接的连杆151，连杆151与滑块152转动连接，滑块152与进气室中部设置的滑杆153 滑移连接，滑块连接有用于控制所述滑块移动的液压机构154。通过液压机构将端盖14打开后与飞机飞行方向呈锐角设置，同时在端盖14的内表面能够对气流起到导向作用使得气流进入到进气室中。同时为了将进入到进气室中的气流更好的导向至喷气发动机4中，进气室沿气流进入方向上设置成收缩状，从而提供导向作用，有利于喷气发动机4的正常工作。
当飞机发动机突然熄火时，飞机驾驶员手动控制飞机，并调整好飞机的飞行姿态，与此同时打开飞机的喷气发动机4，此时飞机发动机能够为飞机提供飞行的动力，此时飞行员控制机翼2使得机翼2能够为飞机尽可能多的提供升力，从而能够减缓飞机的下落速度。此时飞机在喷气发动机44的动力作用下呈动力滑行状态。在此时的飞行过程中，飞行员能够通过控制飞机的升降舵12或是方向舵13调节飞机的俯仰状态和飞行方向。飞行员可选择降落地点，当飞机飞行至降落地点时飞机可进行迫降，迫降时当飞机即将与地面接触时打开充气单元10，从而降低飞机迫降时与地面的冲击力，进一步保障乘客的生命安全全，避免空难的发生。
实施例二：一种空难逃生飞机，如图4和图5所示，包括机身1，在机身1的两侧对称的安装有机翼2，机翼2上对称安装有为飞机提供动力的主发动机3。机身1和机翼2上还均匀设置有隐藏设置的若干降落伞11。同时飞机的尾部还设置有水平尾翼6和垂直尾翼7，水平尾翼6和垂直尾翼7上分别设置有升降舵12和方向舵13。其中升降舵12用于调整飞机的俯仰状态，方向舵13用于调整飞机的飞行方向。
飞机机身1的尾端的下方安装有安装支架8，安装支架8上安装有喷气发动机4，喷气发动机4的喷气方向即喷气发动机4提供的推力方向与机身1的方向平行。将喷气发动机4设置在机身1尾端的下方，并且通过支架将喷气发动机4连 接在机身1上，此时喷气发动机4不仅能够为机身1提供向前的动力，同时能够产生一定的力矩，使得飞机的机头朝上，机头朝上能够避免飞机快速的下降，同时通过机翼2的调节能够增大升力进一步减缓飞机的下落速度。此外，为了降低喷气发动机4对与飞机在正常飞行状态下的影响，在喷气发动机4的前端设置导流罩9，该导流罩9呈流线型设置，因而能够减小飞行的阻力从而能够节省飞机的燃油，该导流罩9能够在喷气发动机4打开前通过飞行员手动控制进行打开。同时能够飞机机身1的底部还设置有在飞机迫降时，用于缓冲冲击力的充气单元10。
当飞机发动机突然熄火时，飞机驾驶员手动控制飞机，并调整好飞机的飞行姿态，打开导流罩9与此同时打开飞机的喷气发动机4，此时飞机发动机能够为飞机提供飞行的动力，此时飞行员控制机翼2使得机翼2能够为飞机尽可能多的提供升力，从而能够减缓飞机的下落速度。此时飞机在喷气发动机4的动力作用下呈动力滑行状态。在此时的飞行过程中，飞行员能够通过控制飞机的升降舵12或是方向舵13调节飞机的俯仰状态和飞行方向。飞行员可选择降落地点，当飞机飞行至降落地点时飞机可进行迫降，打开隐藏在机身1和机翼2上的降落伞11用于进一步降低飞机的速度，当飞机即将与地面接触时打开充气单元10，从而降低飞机迫降时与地面的冲击力，进一步保障乘客的生命安全全，避免空难的发生。
实施例三：一种空难逃生飞机，如图6所示，与实施例二相比，其区别在于，将喷气发动机4更换为火箭发动机5，火箭发动机5连接在飞机尾端的端部位置。
将喷气发动机4更换为火箭发动机5，火箭发动能够在较短的时间内，提供较大的动力，在飞机主发动机3熄火的同时提供大推力，保障了飞机在瞬时间 推力不会突然减小，从而保证飞机飞行状态的稳定，由于火箭发动机5的工作时间较短，其主要作用就是为了避免主发动机3的熄火对于飞机飞行姿态的影响，在飞机飞行姿态稳定后，飞行员可通过控制飞机滑行完成迫降的过程，从而避免空难的产生。
以上所述仅是本发明的优选实施方式，本发明的保护范围并不仅局限于上述实施例，凡属于本发明思路下的技术方案均属于本发明的保护范围。应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理前提下的若干改进和润饰，这些改进和润饰也应视为本发明的保护范围。

Claims (9)

  1. 一种空难逃生飞机，包括有机身(1)以及设置于机身(1)左右两侧的机翼(2)，所述机翼(2)上对称设置有主发动机(3)，其特征在于：所述机身(1)的尾端设置有在所述主发动机(3)熄火后打开的喷气发动机(4)，所述喷气发动机(4)为飞机提供推力。
  2. 根据权利要求1所述的空难逃生飞机，其特征在于：所述喷气发动机(4)位于所述机身(1)尾端的内部，所述机身(1)内设置有与所述喷气发动机连通的进气室，所述进气室上均匀设置有能够在喷气发动机(4)启动前打开的的端盖(14)，所述端盖(14)靠近所述机身(1)的尾端的一端转动连所述机身(1)，所述端盖(14)连接有由于所述端盖(14)启闭的控制机构(15)，所述端盖(14)打开后与飞机飞行方向相对且呈锐角设置。
  3. 根据权利要求2所述的空难逃生飞机，其特征在于：所述控制机构(15)包括所述端盖(14)的内表面转动连接的连杆(151)，所述连杆转动连接有滑块(152)，所述滑块(152)与所述进气室中部设置的滑杆(153)滑移连接，所述滑块(152)连接有用于控制所述滑块移动的液压机构(154)。
  4. 根据权利要求1所述的空难逃生飞机，其特征在于：所述发动机位于所述机身(1)下方，所述喷气发动机(4)连接有安装支架(8)，所述安装支架(8)连接在所述机身(1)尾端的下方。
  5. 根据权利要求1所述的空难逃生飞机，其特征在于：所述喷气发动机(4)可更换为火箭发动机(5)。
  6. 根据权利要求1所述的空难逃生飞机，其特征在于：所述火箭发动机(5)连接在所述机身(1)尾端的端部。
  7. 根据权利要求1所述的空难逃生飞机，其特征在于：所述喷气发动机(4)的前端连接有呈流线型设置用于减小正常飞行时阻力的导流罩(9)，所述导流罩(9)在需要打开所述喷气发动机(4)前打开。
  8. 根据权利要求1所述的空难逃生飞机，其特征在于：所述机身(1)的底部还设置有至少一个用于在飞机迫降时缓冲所述机身(1)冲击力的充气单元(10)。
  9. 根据权利要求1所述的空难逃生飞机，其特征在于：所述机身(1)和或所述机翼(2)上还均匀设置有隐藏设置的若干降落伞(11)。
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